Volume 29 Issue 8
Aug.  2014
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LI Wei, ZHANG Bo, WANG Fei, JI Hong-hu, HUA Jia, ZHANG Zong-bin, LUO Ming-dong. Numerical simulation on infrared radiation characteristics of round to rectangular nozzles with different chevrons considering engine components[J]. Journal of Aerospace Power, 2014, (8): 1810-1816. doi: 10.13224/j.cnki.jasp.2014.08.008
Citation: LI Wei, ZHANG Bo, WANG Fei, JI Hong-hu, HUA Jia, ZHANG Zong-bin, LUO Ming-dong. Numerical simulation on infrared radiation characteristics of round to rectangular nozzles with different chevrons considering engine components[J]. Journal of Aerospace Power, 2014, (8): 1810-1816. doi: 10.13224/j.cnki.jasp.2014.08.008

Numerical simulation on infrared radiation characteristics of round to rectangular nozzles with different chevrons considering engine components

doi: 10.13224/j.cnki.jasp.2014.08.008
  • Received Date: 2013-04-25
  • Publish Date: 2014-08-28
  • Considering the impacts of the center cone, lobe mixer, flame holder and afteburner cavity, the round to rectangular nozzle transition from axial symmetry convergent-divergent nozzle was designed, different chevrons were devised and assembled to the nozzle exit. Numerical simulations were carried on the flow, heat transfer and infrared radiation characteristics. The results indicate that the precision of the infrared radiation intensity distributions were more in line with the actual rules by taking the hot components into account. Compared to the basic round to rectangular nozzle, the length of high-temperature regions decrease with multiple small chevrons and further decreasesd with simple large one, individually. Furthermore, the infrared radiation intensity decreases obviously detected from 0 degree. The plume mixing with ambient flow and infrared suppressing characteristics are enhanced in rectangular nozzle with chevrons from axis one. At the same time, it will cause a little thrust lost.

     

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  • [1]
    张宗斌,桑建华.发动机排气系统红外隐身技术研究[J].隐身技术,2009(3):2-4. ZHANG Zongbin,SANG Jianhua.Research of infrared technology of aeroegine exhaust system[J].Stealth Technology,2009(3):2-4.(in Chinese)
    [2]
    罗明东.无人机排气系统红外隐身技术研究[D].南京:南京航空航天大学,2006. LUO Mingdong.Investigation of infrared stealth technology of the exhaust system for unmanned aerial vehicle[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2006.(in Chinese)
    [3]
    张勃,吉洪湖,罗明东,等,宽高比对尾向可见明火矩形喷管红外抑制特性影响研究[J].航空动力学报,2007,22(11):1820-1825. ZHANG Bo,JI Honghu,LUO Mingdong,et al.Investigation of the effect of aspect ratio to infrared suppressing characteristics of rectangular nozzles[J].Journal of Aerospace Power,2007,22(11):1820-1825.(in Chinese)
    [4]
    张勃,吉洪湖,张宗斌.中心锥冷却对喷管腔体红外辐射的抑制作用数值分析[J].航空动力学报,2007,22(3):560-565. ZHANG Bo,JI Honghu,ZHANG Zongbin,et al.Numerical investigation of infrared radiation characteristics of nozzle cavities with cone cooled[J].Journal of Aerospace Power,2007,22(3):560-565.(in Chinese)
    [5]
    张靖周,单勇.直升机排气系统用波瓣喷管引射-混合式红外抑制器研究[J].航空学报,2007,28(1):32-36. ZHANG Jingzhou,SHAN Yong.Investigation on lobed nozzle mixer-ejector infrared suppressor for helicopter exhaust system[J].Acta Aeronautica et Astronautica Sinica,2007,28(1):32-36.(in Chinese)
    [6]
    张靖周,李立国,高潮,等.波瓣喷管红外抑制系统的实验研究[J].航空动力学报,1997,12(2):212-214. ZHANG Jingzhou,LI Liguo,GAO Chao,et al.An experimental study on a lobed nozzle of an infrared suppression system[J].Journal of Aerospace Power,1997,12(2):212-214.(in Chinese)
    [7]
    张靖周,李立国,高潮,等.直升机排气系统红外抑制器的模型实验研究[J].红外与毫米波学报,2005,24(2):125-129. ZHANG Jingzhou,LI Liguo,GAO Chao,et al.Model experiments of infrared suppressor for helicopter exhaust system[J].Journal of Infrared and Millimeter Waves,2005,24(2):125-129.(in Chinese)
    [8]
    Presz W M,Gousy R G,Morin B L.Forced mixer lobes in ejector designs[R].AIAA 86-21614,1986.
    [9]
    姜卫星,李立国,陈锵.波瓣混合流场流向涡的数值分析[J].航空学报,1998,19(3):318-322. JIANG Weixing,LI Liguo,CHEN Qiang.Numerical analysis of streamwise vorticity in the flow-field of a lobed mixer[J].Acta Aeronautic et Astronautic Sinica,1998,19(3):318-322.(in Chinese)
    [10]
    黄勇,郭志辉,魏福清.收扩喷管加小突片对尾喷流红外辐射的影响[J].航空动力报,2001,16(1):19-22. HUANG Yong,GUO Zhihui,WEI Fuqing.Effect of tabs fixed on a convergent-divergent nozzle on infrared radiation of exhausting jet[J].Journal of Aerospace Power,2001,16(1):19-22.(in Chinese)
    [11]
    Ahuja K K.Mixing enhancement and jet noise reduction through tabs plus ejectors[R].AIAA 93-4347,1993.
    [12]
    Zaman K B M Q,Samimy M.Supersonic jet mixing enhancement by delta-tabs[R].AIAA 92-3548,1992.
    [13]
    Zaman K B M Q.Streamwise vorticity generation and mixing enhancement in free jet by delta-tabs[R].AIAA 93-3253,1993.
    [14]
    Skebe S A,McCormick D C.Parameter effects on mixer-ejector pumping performance[R].AIAA 88-20188,1988.
    [15]
    Bridges J E,Brown C A.Parametric testing of chevrons on single flow hot jets[R].AIAA 2004-22824,2004.
    [16]
    黄宏艳,王强.V形尾缘喷管流场与红外特性的数值模拟[J].北京航空航天大学学报,2008,34(2):158-161. HUANG Hongyan,WANG Qiang.Numerical simulation on flow field and infrared characteristics of chevron nozzles[J].Journal of Beijing University of Aeronautics and Astronautics,2008,34(2):158-161.(in Chinese)
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